CN206871352U - Hybrid power unmanned plane with small rotor - Google Patents
Hybrid power unmanned plane with small rotor Download PDFInfo
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- CN206871352U CN206871352U CN201720090592.XU CN201720090592U CN206871352U CN 206871352 U CN206871352 U CN 206871352U CN 201720090592 U CN201720090592 U CN 201720090592U CN 206871352 U CN206871352 U CN 206871352U
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Abstract
The utility model belongs to unmanned plane field, disclose a kind of hybrid power unmanned plane with small rotor, including fuselage, hollow shaft on fuselage and it is set in hollow shaft and is coaxial therewith the primary spindle of the heart, rotor is connected with primary spindle, lower rotor is connected with hollow shaft, hollow shaft and primary spindle are rotated backward by the drive mechanism driving in fuselage simultaneously, some small rotors are arranged with fuselage, small rotor is rotated by motor driven, motor connection has the power supply in fuselage, power supply is connected with generator, generator is connected to the drive mechanism, drive mechanism and motor are all connected to controlling organization.Pass through above-mentioned generator, the kinetic energy of drive mechanism can be converted into electrical energy transportation and stored to power supply, gone wrong in drive mechanism, when causing rotor and the lower rotor to run out of steam, small rotor wing rotation can be driven by motor, aids in unmanned plane safe falling.
Description
Technical field
It the utility model is related to unmanned air vehicle technique field, more particularly to a kind of hybrid power unmanned plane with small rotor.
Background technology
With the fast development of the development of unmanned air vehicle technique, especially gyroplane technology, its application surface is more and more wider, in the people
Indispensable importance is embodied with field and military domain.
Current several unmanned gyroplanes include single rotor (i.e. helicopter), coaxial anti-oar helicopter and more rotors, wherein
" -50 helicopters of card " of coaxial anti-oar helicopter such as Russia, its operation principle is that the axle of lower rotor is hollow shaft, upper rotor
Axle is concentric to be passed through from hollow shaft, and double-deck rotor diameter size is identical and can be adjusted by blade pitch control mechanism to phase
Same pitch, then by two driven gears above and below umbrella tooth wheel drive, rotor is rotated with opposite rotation direction up and down for drive, two
The opposite other conditions identical rotor in individual direction of rotation can just cancel out each other anti-twisted torque, thus not need tail pipe and tail
Oar.
This design improves unmanned plane power performance to a certain extent, simplifies afterbody design, but this kind design is grasped
Control is complicated, and it needs rotor holding high consistency up and down, i.e., rotor size structure is identical up and down, and pitch also needs completely
Identical, so rotor can cancel out each other anti-twisted torque up and down, and then coaxial anti-oar helicopter is smoothly flown, once occur
During the difference of pitch, upper and lower rotor can not just cancel out each other anti-twisted torque, cause coaxial anti-oar helicopter is out of control can not normally fly
OK, although can now be adjusted the pitch of upper and lower rotor to identical by blade pitch control mechanism, its operation difficulty is larger,
User's manipulation is not easy.
Moreover, above-mentioned coaxial anti-oar helicopter is by the dynamic driven by engine bevel gear of oil, then by umbrella tooth wheel drive above and below
Rotor rotational, according to statistics, the cause of accident of existing coaxial anti-oar helicopter is that the dynamic engine failure of oil makes rotor up and down mostly
Run out of steam, it is uncontrolled so as to cause air crash accident, therefore, how to reduce after the dynamic engine of oil breaks down and even avoid
Accident is one of current problem to be solved.
Utility model content
The purpose of this utility model is to provide a kind of hybrid power unmanned plane with small rotor, existing coaxial to solve
Above mentioned problem existing for anti-oar helicopter.
To use following technical scheme up to this purpose, the utility model：
A kind of hybrid power unmanned plane with small rotor, including fuselage, hollow shaft on fuselage and are arranged
In hollow shaft and the primary spindle of the heart is coaxial therewith, rotor is connected with the primary spindle, is connected with down in the hollow shaft
Rotor, the hollow shaft and primary spindle are rotated backward by the drive mechanism driving in fuselage simultaneously, symmetrical on the fuselage
Provided with some small rotors, the small rotor is rotated by motor driven, and the motor connection has the power supply in fuselage,
The power supply is connected with generator, and the generator is connected to the drive mechanism, and the drive mechanism and motor connect
It is connected to controlling organization.
Preferably, the upper rotor is connected with blade pitch control mechanism away from fixation, the lower rotor.
Preferably, the upper rotor and lower rotor are respectively connected with blade pitch control mechanism.
Preferably, the diameter of the upper rotor is less than the diameter of lower rotor.
Preferably, the oil that the drive mechanism includes being connected to controlling organization moves engine, and by the dynamic hair of the oil
The driving bevel gear of motivation driving, the driving bevel gear, which is engaged with, to be respectively and fixedly connected with hollow shaft and primary spindle and setting up and down
Driven bevel pinion.
Preferably, the generator is connected with the first bevel gear, first bevel gear and two driven bevel pinion phases
Engagement.
Preferably, if the fuselage is circumferentially provided with dry support arm, the motor is arranged on the support arm, and defeated
Go out end and connect the small rotor.
Preferably, the small rotor is provided with 6, the circumference of the fuselage is symmetrically arranged on.
Preferably, the small rotor is horizontally disposed or is with respect to the horizontal plane set in angle.
Preferably, it is arranged with pitch in the hollow shaft.
The utility model is by setting small rotor, can be with when torsional forces difference can be produced between upper rotor and lower rotor
By the rotation of small rotor, to offset, caused torsional forces is poor between upper rotor and lower rotor so that aircraft can normally fly
OK.
By above-mentioned generator, the kinetic energy of drive mechanism can be converted into electrical energy transportation and stored to power supply,
Gone wrong in drive mechanism, when causing rotor and the lower rotor to run out of steam, small rotor wing rotation can be driven by motor, it is auxiliary
Unmanned plane safe falling is helped, when avoiding that rotor and lower rotor run out of steam on existing unmanned plane, causes unmanned plane to fall because out of control
Ruin or injure surface structures and crowd.
Brief description of the drawings
Fig. 1 is the dimensional structure diagram for the hybrid power unmanned plane that the utility model has small rotor；
Fig. 2 is the side view for the hybrid power unmanned plane (hiding fuselage and small rotor) that the utility model has small rotor；
Fig. 3 is the decomposing schematic representation for the hybrid power unmanned plane (hiding fuselage) that the utility model has small rotor.
In figure：
1st, fuselage；2nd, hollow shaft；3rd, primary spindle；4th, upper rotor；5th, lower rotor；6th, drive mechanism；7th, small rotor；8th, it is electric
Machine；9th, power supply；10th, generator；20th, pitch；11st, support arm；61st, the dynamic engine of oil；62nd, driving bevel gear；63rd, from
Dynamic bevel gear；64th, the first bevel gear；65th, belt.
Embodiment
Further illustrate the technical solution of the utility model below in conjunction with the accompanying drawings and by embodiment.
Embodiment one：
The present embodiment provides a kind of hybrid power unmanned plane with small rotor, as Figure 1-3, the hybrid power nobody
Machine includes fuselage 1, in the hollow shaft 2 that the middle position of fuselage 1 is equipped with primary spindle 3 and is set in outside primary spindle 3, the sky
The 3 concentric setting of mandrel 2 and primary spindle.Above-mentioned primary spindle 3 and hollow shaft 2 are driven by the drive mechanism 6 inside fuselage 1 simultaneously
Dynamic synchronous axial system, and primary spindle 3 is opposite with the rotation direction of hollow shaft 2.Rotor 4 is installed on primary spindle 3, and it is small by this
Main shaft 3 drives upper rotor 4 to rotate, and lower rotor 5 is provided with hollow shaft 2, and drive lower rotor 5 to rotate by the hollow shaft 2.It is logical
The reverse rotation of rotor 4 and lower rotor 5 is crossed, realizes the flight of the unmanned plane.
Fig. 2 is can refer to, above-mentioned drive mechanism 6 includes the dynamic engine 61 of oil, and is fixed in the dynamic output end of engine 61 of oil
Driving bevel gear 62, the driving bevel gear 62, which is engaged with, to be respectively and fixedly connected with hollow shaft 2 and primary spindle 3 and setting up and down driven
Bevel gear 63.The above-mentioned dynamic engine 61 of oil is connected with controlling organization (not shown), starts by the way that controlling organization control oil is dynamic
The operation of machine 61, then drive driving bevel gear 62 to rotate by the dynamic engine 61 of oil, so driven by driving bevel gear 62 and its
Two driven bevel pinions 63 synchronous axial system in a reverse direction of engagement, also allows for primary spindle 3 and hollow shaft 2 and drives respectively
Rotor 4 and lower rotor 5 synchronous axial system in a reverse direction, realize the flight of unmanned plane.It should be noted that in the present embodiment,
The above-mentioned dynamic engine 61 of oil can also drive driving bevel gear 62 to rotate (shown in Fig. 3) by belt 65.
In the present embodiment, the diameter of above-mentioned upper rotor 4 is less than the diameter of lower rotor 5, so that the diameter of lower rotor 5 is big
In the downwash flow area of upper rotor 4, the existing coaxial anti-oar class unmanned plane identical caused air-flow phase of the diameter of rotor 5 up and down is avoided
Mutually influence, improve the power performance of unmanned plane.
In the present embodiment, above-mentioned upper rotor 4 is fixedly mounted on primary spindle 3, that is, the pitch fixation of upper rotor 4 can not
Regulation, lower rotor 5 are connected with blade pitch control mechanism (not shown), and the blade pitch control mechanism is used for the oar for adjusting lower rotor 5
Away from.Specifically, the pitch of the present embodiment refers to blade angle, that is, the inclination angle of rotor blade and Plane of rotation, in certain limit
Interior, blade angle is bigger, and the windward side of blade is bigger, and caused lift is bigger, and torsional forces is also bigger, passes through the change of the blade angle
Change, by increasing capacitance it is possible to increase or reduce lower thrust or pulling force caused by rotor 5, so as to realize the control in unmanned plane course.Above-mentioned pitch is adjusted
Section mechanism is prior art, therefore its structure is not repeated herein, as long as the structure of the lower pitch of rotor 5 regulation can be realized,
It may be considered blade pitch control mechanism.
In the present embodiment, because the pitch of upper rotor 4 is fixed, the lower pitch of rotor 5 is adjustable, and the diameter of upper rotor 4 is small
In the diameter of lower rotor 5, rotor 4 and torsional forces difference caused by lower rotor 5 are now inevitably resulted in, torsional forces difference be present
Situation, now, in order to which offset torque power is poor, the balance of unmanned plane is preferably realized, the present embodiment is symmetrically set in the circumference of fuselage 1
If there is dry support arm 11, motor 8 is provided with each support arm 11, can refer to Fig. 2, power supply is provided with fuselage 1
9, above-mentioned power supply 9 is connected to motor 8, for being powered to motor 8.It is more highly preferred to, generating is installed in fuselage 1
Machine 10, the generator 10 engage two driven bevel pinions 63 by the first bevel gear 64, by kinetic energy caused by the dynamic engine 61 of oil
Electric energy is converted into, is conveyed to power supply 9, can also will be unnecessary while now power supply 9 provides electric energy to motor 8
Electrical power storage, with to be used.
In the present embodiment, each motor 8 is all connected to controlling organization, and the output end of each motor 8 is respectively connected with small rotation
The wing 7, and drive the small rotor 7 to rotate.By setting small rotor 7, when there is torsional forces difference, small rotor 7 can be passed through
Rotation it is poor to balance torsional forces caused by upper rotor 4 and lower rotor 5, and then realize the smooth flight of unmanned plane.
In the present embodiment, above-mentioned small rotor 7 is preferably provided with 6, and above-mentioned 6 small rotor 7 rotates simultaneously, passes through control
The speed discrepancy of each small rotor 7 of system, both provided lift for unmanned plane, assists lower rotor 5 to control direction, can balance again
Torsional forces between rotor 4 and lower rotor 5 is poor.
According to statistics, unmanned plane cause of accident is that the dynamic failure of engine 61 of oil makes rotor run out of steam mostly, it is uncontrolled from
And cause air crash accident.And the setting of the above-mentioned small rotor 7 of the present embodiment, cause the He of rotor 4 in the dynamic failure of engine 61 of oil
When lower rotor 5 runs out of steam, small rotor 7 can be driven to rotate by motor 8, aid in unmanned plane safe falling, avoid existing
When rotor 4 and lower rotor 5 run out of steam on unmanned plane, unmanned plane is caused to crash or injure surface structures and crowd because out of control.
In the present embodiment, above-mentioned small rotor 7 is horizontally disposed or is with respect to the horizontal plane set in angle, specifically can be according to need
Set, preferably to realize the lifting of unmanned plane performance.
Above-mentioned controlling organization includes remote manipulator (not shown) and communicates to connect and be located at remote manipulator
Circuit board (not shown) inside fuselage 1, the circuit board be connected to above-mentioned drive mechanism 6, blade pitch control mechanism with
And motor 8.By remote manipulator come remotely pilotless machine two sets of self-driving systems (rotation of i.e. upper rotor 4 and lower rotor 5, with
And the rotation of small rotor 7), enable to two sets of self-driving systems separate, again can be with mutually coordinated auxiliary in work.
In the present embodiment, pitch 20 is arranged with hollow shaft 2, the pitch 20 can coordinate above-mentioned small rotor 7, come more
The heading of the good control hybrid power unmanned plane, because pitch 20 is existing structure, will not be repeated here.
The hybrid power unmanned plane of the present embodiment, by being arranged with some small rotors 7 on the fuselage 1, in the upper He of rotor 4
When torsional forces difference is produced between lower rotor 5, it can be produced by the rotation of small rotor 7 to offset between upper rotor 4 and lower rotor 5
Raw torsional forces is poor so that unmanned plane normal flight.
By only setting blade pitch control mechanism at lower rotor 5, and the upper pitch of rotor 4 is fixed, needed in unmanned plane during flying
, can be by the cooperation of small rotor 7 when adjusting the pitch of lower rotor 5, balance paddle is poor away from the torsional forces that regulation is brought, to cause nothing
Man-machine normal flight, and the present embodiment only needs to control the pitch of lower rotor 5, is not necessary to consider the oar of the upper rotor 4 of control
Away from simplifying the operation difficulty of the coaxial anti-oar design of tradition, user's manipulation gets up to be more prone to.
Embodiment two：
The present embodiment differs only in embodiment one：
In the present embodiment, the pitch of above-mentioned upper rotor 4 is equally adjustable, i.e., it is respectively connected with pitch tune as lower rotor 5
Mechanism is saved, by the blade pitch control mechanism, the pitch of rotor 4 can be adjusted, in order to improve the performance of unmanned plane.Need to refer to
Go out, when upper rotor 4 and lower rotor 5 are provided with blade pitch control mechanism, also occur between rotor 4 and lower rotor 5
The situation of torsional forces difference is produced, now the small rotor 7 in the present embodiment can still offset and be produced between rotor 4 and lower rotor 5
Raw torsional forces is poor so that unmanned plane normal flight.
Remaining structure of the hybrid power unmanned plane of the present embodiment and all same of embodiment one, therefore will not be repeated here.
Obviously, above-described embodiment of the present utility model is used for the purpose of clearly illustrating the utility model example, and
It is not the restriction to embodiment of the present utility model.For those of ordinary skill in the field, in described above
On the basis of can also make other changes in different forms.There is no need and unable to give all embodiments
It is exhaustive.All made within spirit of the present utility model and principle all any modification, equivalent and improvement etc., should be included in
Within the protection domain of the utility model claims.
Claims (10)
1. a kind of hybrid power unmanned plane with small rotor, it is characterised in that including fuselage (1), on fuselage (1)
Hollow shaft (2) and it is set in hollow shaft (2) and is coaxial therewith the primary spindle (3) of the heart, is connected with the primary spindle (3)
Rotor (4), lower rotor (5), the hollow shaft (2) and primary spindle (3) are connected with while by positioned at fuselage on the hollow shaft (2)
(1) drive mechanism (6) driving in is rotated backward, and some small rotors (7), the small rotor are arranged with the fuselage (1)
(7) driven and rotated by motor (8), the motor (8) is connected with the power supply (9) in fuselage (1), the power supply electricity
Source (9) is connected with generator (10), and the generator (10) is connected to the drive mechanism (6), the drive mechanism (6) and electricity
Machine (8) is all connected to controlling organization.
2. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that the upper rotor (4)
Pitch is fixed, and the lower rotor (5) is connected with blade pitch control mechanism.
3. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that the upper rotor (4)
Blade pitch control mechanism is respectively connected with lower rotor (5).
4. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that the upper rotor (4)
Diameter be less than lower rotor (5) diameter.
5. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that the drive mechanism
(6) oil for including being connected to controlling organization moves engine (61), and the active umbrella tooth by dynamic engine (61) driving of the oil
Take turns (62), the driving bevel gear (62), which is engaged with, to be respectively and fixedly connected with hollow shaft (2) and primary spindle (3) and setting up and down driven
Bevel gear (63).
6. the hybrid power unmanned plane according to claim 5 with small rotor, it is characterised in that the generator (10)
The first bevel gear (64) is connected with, first bevel gear (64) is meshed with two driven bevel pinions (63).
7. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that fuselage (1) week
To if dry support arm (11) is provided with, the motor (8) is arranged on the support arm (11), and output end connects the small rotation
The wing (7).
8. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that the small rotor (7)
6 are provided with, is symmetrically arranged on the circumference of the fuselage (1).
9. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that the small rotor (7)
It is horizontally disposed with or is with respect to the horizontal plane set in angle.
10. the hybrid power unmanned plane according to claim 1 with small rotor, it is characterised in that the hollow shaft (2)
On be arranged with pitch (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720090592.XU CN206871352U (en) | 2017-01-24 | 2017-01-24 | Hybrid power unmanned plane with small rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720090592.XU CN206871352U (en) | 2017-01-24 | 2017-01-24 | Hybrid power unmanned plane with small rotor |
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| Publication Number | Publication Date |
|---|---|
| CN206871352U true CN206871352U (en) | 2018-01-12 |
Family
ID=61326397
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720090592.XU Active CN206871352U (en) | 2017-01-24 | 2017-01-24 | Hybrid power unmanned plane with small rotor |
Country Status (1)
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| CN (1) | CN206871352U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109515743A (en) * | 2018-10-17 | 2019-03-26 | 中国特种飞行器研究所 | A kind of helicopter ditching model rotor lift simulator |
| CN110566397A (en) * | 2019-09-12 | 2019-12-13 | 大连理工大学 | tidal current energy power generation system based on coaxial contra-rotating propeller technology |
-
2017
- 2017-01-24 CN CN201720090592.XU patent/CN206871352U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109515743A (en) * | 2018-10-17 | 2019-03-26 | 中国特种飞行器研究所 | A kind of helicopter ditching model rotor lift simulator |
| CN109515743B (en) * | 2018-10-17 | 2022-05-27 | 中国特种飞行器研究所 | Helicopter overwater forced landing model rotor lift force simulation device |
| CN110566397A (en) * | 2019-09-12 | 2019-12-13 | 大连理工大学 | tidal current energy power generation system based on coaxial contra-rotating propeller technology |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221008 Address after: Room 105, Building 9, Area B3 (formerly Area 2 of Ronghui Business Park), Enterprise Headquarters Base, Binhai-Zhongguancun Science and Technology Park, Economic and Technological Development Zone, Binhai New Area, Tianjin 300457 Patentee after: Tianjin Phoenix Intelligent Technology Co.,Ltd. Address before: Floor 1, block B, No.3, Tengfei Road, Junliang City, Dongli District, Tianjin Patentee before: TIANJIN SHUGUANG TIANCHENG TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |